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There are a total of 31 record(s) matching your query.
Sorted by: Date Added To NTRS in Descending order
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Low-speed aerodynamic characteristics of a hypersonic research airplane concept having a 70 deg swept delta wing
Author(s): Creel, T. R., Jr.; Penland, J. A.
Abstract: An experimental investigation of the low-speed static longitudinal, lateral and directional stability characteristics of a hypersonic research airplane concept having a 70 deg swept delta wing was conducted in a low-speed ...
NASA Center: Langley Research Center
Publication Year: 1974
Added to NTRS: 2008-06-27
Accession Number: 74N31485; Document ID: 19740023372; Report Number: NASA-TM-X-71974
Aerodynamic heating at Mach 8 of attached inflatable decelerator configurations
Author(s): Creel, T. R., Jr.; Miserentino, R.
Abstract: Mach 8 variable-density tunnel used for determination of aerodynamic heating of attached inflatable decelerator configurations
NASA Center: Langley Research Center
Publication Year: 1971
Added to NTRS: 2008-04-01
Accession Number: 71N38758; Document ID: 19710029282; Report Number: L-7864, NASA-TM-X-2355
Sound shield
Author(s): Creel, T. R., Jr.
Abstract: An improved test section for a supersonic or hypersonic wind tunnel is disclosed wherein the model tested is shielded from the noise normally radiated by the turbulent tunnel wall boundary layer. A vacuum plenum surrounds ...
NASA Center: Langley Research Center
Publication Year: 1982
Added to NTRS: 2008-01-25
Accession Number: 83N17235; Document ID: 19830008964
Apparatus for determining thermophysical properties of test specimens
Author(s): Creel, T. R., Jr.; Jones, R. A.; Corwin, R. R.
Abstract: Apparatus is described for directly measuring the quantity square root of pck of a test specimen such as a wind tunnel model where p is density, c is the specific heat and k is the thermal conductivity of the specimen. The ...
NASA Center: Langley Research Center
Publication Year: 1977
Added to NTRS: 2008-01-24
Accession Number: 77N27131; Document ID: 19770020187
Longitudinal aerodynamic characteristics of a tension shell entry configuration at Mach 20
Author(s): Creel, T. R., Jr.
Abstract: Longitudinal aerodynamic characteristics of tension shell entry configuration at Mach 20
NASA Center: Langley Research Center
Publication Year: 1966
Added to NTRS: 2006-11-06
Accession Number: 66N33452; Document ID: 19660024162; Report Number: NASA-TN-D-3541
Calibration experience in the Langley hotshot tunnel for Mach numbers from 12 to 26
Author(s): Creel, T. R., Jr.; Miller, C. G., III; Smith, F. M.
Abstract: Arc chamber results on effects of rocket nozzle throat diameter and nozzle axial station on flow characteristics for Mach numbers from 12 to 26
NASA Center: Langley Research Center
Publication Year: 1966
Added to NTRS: 2006-11-06
Accession Number: 66N16559; Document ID: 19660007270; Report Number: NASA-TN-D-3278
Correlations of supersonic boundary-layer transition on cones including effects of large axial variations in wind-tunnel noise
Author(s): Chen, F. J.; Beckwith, I. E.; Creel, T. R., Jr.
Abstract: Transition data on sharp tip cones in two pilot low disturbance wind tunnels at Mach numbers of 3.5 and 5 were correlated in terms of noise parameters with data from several conventional wind tunnels and with data from ...
NASA Center: Langley Research Center
Publication Year: 1984
Added to NTRS: 2005-10-13
Accession Number: 84N17534; Document ID: 19840009466; Report Number: L-15669, NAS 1.60:2229, NASA-TP-2229
Aerodynamic characteristics of a hypersonic research airplane concept having a 70 deg swept double-delta wing at Mach number 0.2
Author(s): Penland, J. A.; Creel, T. R., Jr.; Dillon, J. L.
Abstract: A wind-tunnel of the static longitudinal, lateral and directional stability characteristics of a hypersonic research airplane concept having a 70 deg swept double-delta wing was conducted in the Langley low-turbulence ...
NASA Center: Langley Research Center
Publication Year: 1978
Added to NTRS: 2005-10-13
Accession Number: 78N31045; Document ID: 19780023102; Report Number: L-12215, NASA-TP-1252
Noise reduction in a Mach 5 wind tunnel with a rectangular rod-wall sound shield
Author(s): Creel, T. R., Jr.; Keyes, J. W.; Beckwith, I. E.
Abstract: A rod wall sound shield was tested over a range of Reynolds numbers of 0.5 x 10 to the 7th power to 8.0 x 10 to the 7th power per meter. The model consisted of a rectangular array of longitudinal rods with boundary-layer ...
NASA Center: Langley Research Center
Publication Year: 1980
Added to NTRS: 2005-10-13
Accession Number: 80N26622; Document ID: 19800018123; Report Number: L-13451, NASA-TP-1672
Free-stream noise and transition measurements on a cone in a Mach 3.5 pilot low-disturbance tunnel
Author(s): Beckwith, I. E.; Creel, T. R., Jr.; Chen, F. J.; Kendall, J. M.
Abstract: A small scale Mach 3.5 wind tunnel incorporating certain novel design features and intended for boundary-layer-transition research has been tested. The free stream noise intensities and spectral distributions were determined ...
NASA Center: Langley Research Center
Publication Year: 1983
Added to NTRS: 2005-10-13
Accession Number: 83N34229; Document ID: 19830025958; Report Number: L-15610, NAS 1.60:2180, NASA-TP-2180
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